EP1553203B1 - Method for producing hollow airfoils, also to produce a rotor with hollow airfoils - Google Patents

Method for producing hollow airfoils, also to produce a rotor with hollow airfoils Download PDF

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Publication number
EP1553203B1
EP1553203B1 EP04030231A EP04030231A EP1553203B1 EP 1553203 B1 EP1553203 B1 EP 1553203B1 EP 04030231 A EP04030231 A EP 04030231A EP 04030231 A EP04030231 A EP 04030231A EP 1553203 B1 EP1553203 B1 EP 1553203B1
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EP
European Patent Office
Prior art keywords
carried out
hollow
rotor
produce
material deposition
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Expired - Fee Related
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EP04030231A
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German (de)
French (fr)
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EP1553203A1 (en
Inventor
Erwin Dr. Bayer
Ulrich Dr. Knott
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of EP1553203A1 publication Critical patent/EP1553203A1/en
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Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/20—Manufacture essentially without removing material
    • F05B2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05B2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05B2230/239—Inertia or friction welding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/311—Layer deposition by torch or flame spraying
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/313—Layer deposition by physical vapour deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/314—Layer deposition by chemical vapour deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a method for producing hollow blades, in particular for gas turbines. Furthermore, the invention relates to a method for producing a rotor with hollow blades.
  • SPF DB method As a manufacturing method for hollow blades from the prior art, the so-called SPF (Super Plastic Forming) DB (Diffusion Bonding) method (hereinafter referred to as SPF DB method) known.
  • SPF DB method SPF DB process
  • at least three elements are joined together by diffusion bonding, with two outer elements serving to form the outer walls of the hollow blade and a middle element to provide a support structure.
  • the three elements joined together by diffusion bonding are superplastically reshaped by inflation such that a hollow blade results with the desired blade profile.
  • the hollow blades are assembled from two half-shells, wherein the two half-shells are already arched in the sense of the desired blade profile.
  • From the EP-A-0 451 512 is a method for producing blades, in particular for gas turbines such as aircraft engines, with the following steps: a) providing a shaped body; b) coating the shaped body with a metallic cover layer by material deposition, c) reworking the cover layer to blade surfaces with defined profiling.
  • the present invention is based on the problem to propose a novel method for the production of hollow blades.
  • This problem is solved by a method having the features of claim 1.
  • the method comprises at least the following steps: a) providing a shaped body formed of a porous material such as a metal foam or a felt, b) coating the shaped body with a metallic covering layer of titanium or of a titanium alloy by material deposition, c) reworking the Covering layer to blade surfaces with defined profiling.
  • a support body is provided with a stabilizing edge as a molded body, wherein the stabilizing edge forms a front edge and a rear edge of the hollow blade to be produced. This makes it possible to increase the bird strike resistance of the hollow blade produced.
  • a shaped body for the hollow blade is provided in a first step of the method according to the invention.
  • the shaped body is preferably a supporting body with a stabilizing edge, wherein the stabilizing edge is preferably designed as a sheet metal edge, which extends in the region of a front edge and a rear edge or a flow inlet edge and flow outlet edge of the hollow blade to be produced.
  • the stabilizing edge or edge of the sheet increases the strength of the hollow blade to be produced against bird impact.
  • the support body may be made of porous material, in particular of a felt-like material or of metal foam. Furthermore, the support body may consist of a honeycomb structure, which is covered by a film-like shell.
  • the shaped body provided above is coated with a metallic covering layer of titanium or of a titanium alloy by material deposition.
  • the deposition is preferably carried out by thermal spraying, in particular by low-pressure plasma spraying or by kinetic cold compacting or by vapor deposition of the material by means of a directional material vapor cloud.
  • thermal spraying in particular by low-pressure plasma spraying or by kinetic cold compacting or by vapor deposition of the material by means of a directional material vapor cloud.
  • the cover layer thus provided is subjected to a post-processing in a third step of the method according to the invention in order ultimately to provide a hollow blade whose blade surfaces have a defined profiling.
  • the post-processing can be done by an electrochemical process, called ECM processing, or by a mechanical process, such as vibratory finishing.
  • the rotor carrier may be to act a ring or a disc, wherein the hollow blades are preferably joined by linear friction welding to the rotor carrier.
  • annular rotor carrier is a bling (Bl aded R ing), with a disc-shaped rotor support a blisk (B laded D isc) is so created.
  • both the shaped body for the hollow blades and the rotor carrier can be made of an MMC material.
  • the fatigue strength of the hollow blade or the integrally bladed rotor can be improved. This also increases the bird strike resistance of the produced gas turbine component.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die Erfindung betrifft ein Verfahren zur Herstellung von Hohlschaufeln, insbesondere für Gasturbinen. Des Weiteren betrifft die Erfindung ein Verfahren zur Herstellung eines Rotors mit Hohlschaufeln.The invention relates to a method for producing hollow blades, in particular for gas turbines. Furthermore, the invention relates to a method for producing a rotor with hollow blades.

Moderne Gasturbinen, insbesondere Flugtriebwerke, müssen höchsten Ansprüchen im Hinblick auf Zuverlässigkeit, Gewicht, Leistung, Wirtschaftlichkeit und Lebensdauer gerecht werden. In den letzten Jahrzehnten wurden insbesondere auf dem zivilen Sektor Flugtriebwerke entwickelt, die den obigen Anforderungen voll gerecht werden und ein hohes Maß an technischer Perfektion erreicht haben. Bei der Entwicklung von Flugtriebwerken spielt unter anderem die Werkstoffauswahl, die Suche nach neuen, geeigneten Werkstoffen sowie die Suche nach neuen Fertigungsverfahren eine entscheidende Rolle.Modern gas turbines, in particular aircraft engines, must meet the highest demands in terms of reliability, weight, performance, economy and service life. In recent decades, aircraft engines have been developed, particularly in the civil sector, which fully meet the above requirements and have achieved a high degree of technical perfection. Among other things, the selection of materials, the search for new, suitable materials and the search for new production processes play a crucial role in the development of aircraft engines.

Zur Reduzierung des Gewichts von Gasturbinenbauteilen ist es aus dem Stand der Technik bereits bekannt, Schaufeln von Gasturbinen als Hohlschaufeln auszubilden. Die Schaufeln von Gasturbinen tragen nämlich maßgeblich zum Gewicht einer Gasturbine bei. Je stärker das Gewicht der Gasturbine reduziert werden kann, desto günstiger fällt das sogenannte Schub-Gewichtsverhältnis des Flugtriebwerks aus, welches ein entscheidendes Wettbewerbsmerkmal für Flugtriebwerke darstellt.To reduce the weight of gas turbine components, it is already known from the prior art to form blades of gas turbines as hollow blades. The blades of gas turbines contribute significantly to the weight of a gas turbine. The stronger the weight of the gas turbine can be reduced, the more favorable is the so-called thrust-weight ratio of the aircraft engine, which represents a decisive competitive feature for aircraft engines.

Als Herstellverfahren für Hohlschaufeln ist aus dem Stand der Technik das sogenannte SPF (Super Plastic Forming) DB (Diffusion Bonding)-Verfahren (nachfolgend kurz SPF DB-Verfahren genannt) bekannt. Beim SPF DB-Verfahren werden mindestens drei Elemente durch Diffusionsschweißen miteinander verbunden, wobei zwei äußere Elemente der Bildung der Außenwände der Hohlschaufel und ein mittleres Element der Bereitstellung einer Stützkonstruktion dient. Die drei miteinander durch Diffusionsschweißen verbundenen Elemente werden durch Aufblasen bzw. Aufblähen derart superplastisch umgeformt, dass sich eine Hohlschaufel mit dem gewünschten Schaufelprofil ergibt.As a manufacturing method for hollow blades from the prior art, the so-called SPF (Super Plastic Forming) DB (Diffusion Bonding) method (hereinafter referred to as SPF DB method) known. In the SPF DB process, at least three elements are joined together by diffusion bonding, with two outer elements serving to form the outer walls of the hollow blade and a middle element to provide a support structure. The three elements joined together by diffusion bonding are superplastically reshaped by inflation such that a hollow blade results with the desired blade profile.

Nach einem anderen, aus dem Stand der Technik bekannten Verfahren zur Herstellung von Hohlschaufeln werden die Hohlschaufeln aus zwei Halbschalen zusammengefügt, wobei die beiden Halbschalen bereits im Sinne des gewünschten Schaufelprofils gewölbt sind.According to another, known from the prior art method for producing hollow blades, the hollow blades are assembled from two half-shells, wherein the two half-shells are already arched in the sense of the desired blade profile.

Aus der EP-A-0 451 512 ist ein Verfahren zum Herstellung von Schaufeln, insbesondere für Gasturbinen wie Flugtriebwerke, mit folgenden Schritten bekannt: a) Bereitstellen eines Formkörpers; b) Überziehen des Formkörpers mit einer metallischen Deckschicht durch Materialabscheidung, c) Nachbearbeiten der Deckschicht zu Schaufeloberflächen mit definierter Profilierung.From the EP-A-0 451 512 is a method for producing blades, in particular for gas turbines such as aircraft engines, with the following steps: a) providing a shaped body; b) coating the shaped body with a metallic cover layer by material deposition, c) reworking the cover layer to blade surfaces with defined profiling.

Hinsichtlich weiteren Standes der Technik sei auf die DE-A1-196 09 690 , auf die EP-A-1 070 769 und auf die US-A-5 547 769 verwiesen, die allesamt Verfahren zum Abscheiden von metallischen Schichten auf Hohlschaufeln offenbaren. Die DE-A1-38 31 692 betrifft ein Fügeverfahren für Schaufeln.With regard to other prior art is on the DE-A1-196 09 690 , on the EP-A-1 070 769 and on the US-A-5 547 769 all of which disclose methods for depositing metallic layers on hollow blades. The DE-A1-38 31 692 relates to a joining method for blades.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zur Herstellung von Hohlschaufeln vorzuschlagen. Dieses Problem wird durch ein Verfahren mit den Merkmalen des Patentanspruchs 1 gelöst. Erfindungsgemäß umfasst das Verfahren zumindest die folgenden Schritte: a) Bereitstellen eines als Stützkörper ausgebildeten Formkörpers aus einem porösem Material wie einem Metallschaum oder einem Filz, b) Überziehen des Formkörpers mit einer metallischen Deckschicht aus Titan oder aus einer Titanlegierung durch Materialabscheidung, c) Nachbearbeiten der Deckschicht zu Schaufeloberflächen mit definierter Profilierung.On this basis, the present invention is based on the problem to propose a novel method for the production of hollow blades. This problem is solved by a method having the features of claim 1. According to the invention, the method comprises at least the following steps: a) providing a shaped body formed of a porous material such as a metal foam or a felt, b) coating the shaped body with a metallic covering layer of titanium or of a titanium alloy by material deposition, c) reworking the Covering layer to blade surfaces with defined profiling.

Nach einer vorteilhaften Weiterbildung der Erfindung wird als Formkörper ein Stützkörper mit einem Stabilisierungsrand bereitgestellt, wobei der Stabilisierungsrand eine Vorderkante und eine Rückkante der herzustellenden Hohlschaufel bildet. Hierdurch lässt sich die Vogelschlagfestigkeit der hergestellten Hohlschaufel erhöhen.According to an advantageous embodiment of the invention, a support body is provided with a stabilizing edge as a molded body, wherein the stabilizing edge forms a front edge and a rear edge of the hollow blade to be produced. This makes it possible to increase the bird strike resistance of the hollow blade produced.

Das erfindungsgemäße Verfahren zur Herstellung eines Rotors mit Hohlschaufeln ist im Patentanspruch 8 definiert.The inventive method for producing a rotor with hollow blades is defined in claim 8.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung.Preferred embodiments of the invention will become apparent from the dependent claims and the description below.

Zur Herstellung der erfindungsgemäßen Hohlschaufel wird in einem ersten Schritt des erfindungsgemäßen Verfahrens ein Formkörper für die Hohlschaufel bereitgestellt. Bei dem Formkörper handelt es sich um einen Stützkörper vorzugsweise mit einem Stabilisierungsrand, wobei der Stabilisierungsrand vorzugsweise als Blechrand ausgebildet ist, der im Bereich einer Vorderkante sowie einer Rückkante bzw. einer Strömungseintrittskante sowie Strömungsaustrittskante der herzustellenden Hohlschaufel verläuft.To produce the hollow blade according to the invention, a shaped body for the hollow blade is provided in a first step of the method according to the invention. The shaped body is preferably a supporting body with a stabilizing edge, wherein the stabilizing edge is preferably designed as a sheet metal edge, which extends in the region of a front edge and a rear edge or a flow inlet edge and flow outlet edge of the hollow blade to be produced.

Der Stabilisierungsrand bzw. Blechrand erhöht die Festigkeit der herzustellenden Hohlschaufel gegenüber Vogeleinschlag. Der Stützkörper kann aus porösem Material, insbesondere aus einem filzartigen Material oder aus Metallschaum hergestellt sein. Weiterhin kann der Stützkörper aus einer Honigwabenstruktur bestehen, die von einer folienartigen Hülle überzogen ist.The stabilizing edge or edge of the sheet increases the strength of the hollow blade to be produced against bird impact. The support body may be made of porous material, in particular of a felt-like material or of metal foam. Furthermore, the support body may consist of a honeycomb structure, which is covered by a film-like shell.

In einem zweiten Schritt des erfindungsgemäßen Verfahrens wird der oben bereitgestellte Formkörper mit einer Metallischen Deckschicht aus Titan oder aus einer Titanlegierung durch Materialabscheidung überzogen. Das Abscheiden erfolgt vorzugsweise durch thermisches Spritzen, insbesondere durch Niederdruckplasmaspritzen oder durch kinetisches Kaltkompaktieren oder durch Aufdampfen des Materials mithilfe einer gerichteten Materialdampfwolke. Die Details dieser Materialabscheideverfahren sind dem hier angesprochenen Fachmann geläufig und es bedarf daher keiner näheren Erläuterung derselben.In a second step of the method according to the invention, the shaped body provided above is coated with a metallic covering layer of titanium or of a titanium alloy by material deposition. The deposition is preferably carried out by thermal spraying, in particular by low-pressure plasma spraying or by kinetic cold compacting or by vapor deposition of the material by means of a directional material vapor cloud. The details of these material deposition methods are familiar to the person skilled in the art and therefore no further explanation is required.

Im Anschluss an die Materialabscheidung auf den Formkörper wird die so bereitgestellte Deckschicht in einem dritten Schritt des erfindungsgemäßen Verfahrens einer Nachbearbeitung unterzogen, um letztendlich eine Hohlschaufel bereitzustellen, deren Schaufeloberflächen eine definierte Profilierung aufweisen. Die Nachbearbeitung kann durch ein elektrochemisches Verfahren, eine sogenannte ECM-Bearbeitung, erfolgen oder auch durch ein mechanisches Verfahren, wie zum Beispiel Gleitschleifen.Subsequent to the material deposition onto the shaped body, the cover layer thus provided is subjected to a post-processing in a third step of the method according to the invention in order ultimately to provide a hollow blade whose blade surfaces have a defined profiling. The post-processing can be done by an electrochemical process, called ECM processing, or by a mechanical process, such as vibratory finishing.

Mehrere auf die oben beschriebene Art und Weise hergestellte Hohlschaufeln können in einer Weiterbildung des erfindungsgemäßen Verfahrens zur Herstellung eines integral beschaufelten Rotors an einen Rotorträger gefügt werden. Bei dem Rotorträger kann es sich um einen Ring oder eine Scheibe handeln, wobei die Hohlschaufeln vorzugsweise durch lineares Reibschweißen an den Rotorträger gefügt werden. Bei einem ringförmigen Rotorträger wird so ein Bling (Bladed Ring), bei einem scheibenförmigen Rotorträger wird so ein Blisk (Bladed Disc) geschaffen.Several hollow blades produced in the manner described above can be joined to a rotor carrier in a development of the method according to the invention for producing an integrally bladed rotor. The rotor carrier may be to act a ring or a disc, wherein the hollow blades are preferably joined by linear friction welding to the rotor carrier. In an annular rotor carrier is a bling (Bl aded R ing), with a disc-shaped rotor support a blisk (B laded D isc) is so created.

An dieser Stelle sei abschließend darauf hingewiesen, dass sowohl der Formkörper für die Hohlschaufeln als auch der Rotorträger aus einem MMC-Werkstoff hergestellt sein können. Hierdurch kann die Schwingfestigkeit der Hohlschaufel bzw. des integral beschaufelten Rotors verbessert werden. Auch erhöht sich hierdurch nochmals die Vogelschlagfestigkeit des hergestellten Gasturbinenbauteils.At this point, it should be pointed out that both the shaped body for the hollow blades and the rotor carrier can be made of an MMC material. As a result, the fatigue strength of the hollow blade or the integrally bladed rotor can be improved. This also increases the bird strike resistance of the produced gas turbine component.

Claims (9)

  1. Method for the production of hollow airfoils, in particular for gas turbines such as aircraft engines, comprising the following steps:
    a) the provision of a moulded body designed as a support body and made of a porous material such as a metal foam or felt,
    b) the coating of the moulded body with a metallic finish coating of titanium or a titanium alloy by material deposition,
    c) the reworking of the finish coating to produce airfoil surfaces with a defined profiling.
  2. Method according to claim 1,
    characterised in that
    the support body has a stabilising edge forming a front edge and a rear edge of the hollow airfoil to be produced.
  3. Method according to claim 1 or 2,
    characterised in that
    the material deposition is carried out by thermal spraying, in particular by low-pressure plasma spraying.
  4. Method according to claim 1 or 2,
    characterised in that
    the material deposition is carried out by kinetic cold compacting.
  5. Method according to claim 1 or 2,
    characterised in that
    the material deposition is carried out by vapour deposition by means of a directed material vapour cloud.
  6. Method according to one or more of claims 1 to 5,
    characterised in that
    the reworking of the finish coating to produce airfoil surfaces is carried out by electro-chemical machining (ECM).
  7. Method according to one or more of claims 1 to 5,
    characterised in that
    the reworking of the finish coating to produce airfoil surfaces is carried out by barrel finishing.
  8. Method for the production of a rotor with hollow airfoils, in particular of an integrally bladed gas turbine rotor, comprising the following steps:
    a) the provision of at least one hollow airfoil by using a method according to one or more of claims 1 to 7,
    b) the assembly of a plurality of such hollow airfoils on a disk-shaped or annular rotor support.
  9. Method according to claim 8,
    characterised in that
    the assembly is carried out by linear friction welding.
EP04030231A 2004-01-10 2004-12-21 Method for producing hollow airfoils, also to produce a rotor with hollow airfoils Expired - Fee Related EP1553203B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004001575 2004-01-10
DE102004001575A DE102004001575A1 (en) 2004-01-10 2004-01-10 Method for producing hollow blades and a rotor with hollow blades

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US7766623B2 (en) 2006-11-08 2010-08-03 General Electric Company System for manufacturing a rotor having an MMC ring component and an airfoil component having monolithic airfoils
US7775772B2 (en) 2006-11-08 2010-08-17 General Electric Company System for manufacturing a rotor having an MMC ring component and an airfoil component having MMC airfoils
US7784182B2 (en) 2006-11-08 2010-08-31 General Electric Company System for manufacturing a rotor having an MMC ring component and a unitary airfoil component
DE102008058141A1 (en) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Method for producing a blade for a rotor of a turbomachine
DE102008058142A1 (en) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Method for producing and / or repairing a rotor of a turbomachine and rotor for this purpose
DE102009049707A1 (en) * 2009-10-17 2011-07-28 MTU Aero Engines GmbH, 80995 Method for producing a rotor or stator blade and such a blade
DE102010006907B4 (en) 2010-02-05 2013-10-10 MTU Aero Engines AG Method for producing a hollow component for a gas turbine

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DE3831692A1 (en) 1988-09-17 1989-03-02 Bbc Brown Boveri & Cie Method for connecting the cover plate and/or foot piece on the one hand to the blade on the other by means of a brazing or jointing process
DK0451512T3 (en) 1990-04-11 1993-12-27 Asea Brown Boveri Method of coating buckets
KR950703669A (en) 1992-10-05 1995-09-20 디터 크리스트, 게르하르트 퀼 PROTECTION OF CHROMIUM-STEEL SUBSTRATES AGHINST CORROSIVE AND EROSIVE ATTACK AT TEMPERATURES UP TO ABOUT 500 ℃
DE19609690C2 (en) 1996-03-13 2000-12-28 Karlsruhe Forschzent Turbine blade
DE19934418A1 (en) 1999-07-22 2001-01-25 Abb Alstom Power Ch Ag Process for coating a locally differently stressed component

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